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From ATV to ATV Evolution

February 2004

Hans-Jörg Heidmann

Transportation for In-Orbit Infrastructure and beyond

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ISS ATTITUDE CONTROL

Major features of ATV mission

GYRODYNES/CMG DESATURATION

RETRIEVAL OF WASTE AND DESTRUCTION DURING REENTRY

ISS REFUELING

DRY CARGO

WATER AND GAS

ISS ORBIT CONTROL

DEBRIS AVOIDANCE BY

ISS

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General layout and characteristics

Mass = 20.5 tons at launch

• dry mass : 11 tons

• gross cargo : 9.5 tons

• up to 8 tons of propellant at launch

Sizes

• 10.3 m length

• 4.5 m diameter

• 22.3 m with deployed solar wings (4.8 kW)

• 22 m3 pressurized module (16 m3 for pressurized cargo)

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ATV subsystems

• Power supply : - 4 independent distribution chains with rotative solar panels (Si) and rechargeable batteries (NiCd)

• Data Management System : - 3 Failure Tolerant Computers running the main Flight Applicative Software

• Monitoring and Safety Chain : - 2 independent and autonomous chains for Rendezvous monitoring and Collision Avoidance Maneuver with specific means (data processor, category A software, primary power sources, thrusters…)

• Propulsion Subsystem : - 28 ACS thruster (240N) - 4 OCS thrusters (490 N)- 8 propellant tanks (8 tons of MON + MMH)

• Semi passive TCS : - 40 Variable Conductance Heat Pipes

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ATV subsystems (cont’d)

• External Rendezvous monitoring by the ISS : - Visual Video Target- RF Kurs navigation transponder - Visual Ranging Cues

• Navigation and Monitoring of RV :- Relative GPS- Laser sensors (2 Telegoniometer + 2 Videometers)

• General navigation equipment : - Star Tracker, Accelerometer, Gyrometer, Sun Sensor for survival

• Communication subsystem : - 2 chains compatible TDRSS/Artemis for ATV-CC - 2 chains (S-band) for proximity link with ISS

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ATV subsystems (cont’d)

• Pressurized Module : - 22 m3 pressurized module- up to 8 Standard Racks

- Environment and Control Life Support (fan, smoke detector, light)

• Unpressurized Cargo Tanks : - 3 water tanks- 3 Gas tanks- 2 refueling kits

• Russian Docking System : - Active Docking Unit featuring mechanical, fluidic, electrical and

data interface

• Russian Equipment Control Set : - 2 redundant equipment chains to control interfaces with ISS

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ESAESA

ATV Flight Segment Prime Contractorship.System engineering.Verification of ATV FS.Development of Flight Software.Development and Procurement of Propulsion and Reboost subsystem and of Avionics Chains. ATV assembly, integration and testing.Support to ESA for external interfaces.

Cargo Carrier development and integration.Russian equipment set procurementThermal control studies.

Development of Spacecraft structure subsystem.

Development of Solar Generation subsystem.

EADS-ST (F+D)EADS-ST (F+D)

ATV INDUSTRIAL TEAM

Development of Videometer and Star Tracker.

Development of Telegoniometer

ALENIA SPAZIO (I)ALENIA SPAZIO (I)

CONTRAVES SPACE (CH)CONTRAVES SPACE (CH)

DUTCH SPACE (NL)DUTCH SPACE (NL)

EADS SODERN (F)EADS SODERN (F)

DJO (D)DJO (D)

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1st ATV flight model at overall integration

EquippedAvionics Bay

IntegratedCargo Carrier

EquippedPropulsion Bay

Launcher adapterwith separation system

ATV sub-assembliesdelivered at EADS-ST Bremen - Nov. 2003

1st ATV launch by Ariane 5 (Jules-Verne)

scheduled May 2005

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Servicing of the US-Segment

The NASA Shuttle fleet will be retired from up to 2010, which could lead to a logistical gap for the ISS at least until 2014

This logistical gap could be overcome by ATV derived unmanned transportation vehicles such as:

- ATV Download System

- Cargo Capsule System

- Unpressurized Logistic Carrier

For the logistic supply of the US-Segment by ATV could be developed a special docking mechanism called IBDM (International Docking and Berthing Mechanism).

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2. Scenario Description (6) PTV Scenario

•Lift-off•Separation of Ariane 5 EAPs•Fairing jettisoning•Separation of the EPC•Ignition of the ESP•Separation of the ESP•Separation completed•PTV attitude stabilized•Solar panels deployed•Antennas deployed•Check-up by the PTV control centre•Transfer to the phasing orbit

•Maneuver 1•Drift period 1•Maneuver 2

•Phasing•Drift period 2•Mid course correction•Drift period 3

•Transfer to the ISS vicinity – •Interface with the RV scenario

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-V-bar Approach Scenario

RF linkvolume

Approach ellipsoid

Stabilisation burn2 burn transfer

closingFinal approach

drift

S2S3

RF linkvolume

Approach ellipsoid

Stabilisation burn2 burn transfer

closingFinal approach

drift

S2S3

GPSRFSTR

VDM

+V-BAR APPROACH SCENARIO

YAW REORIENTATION

GPSRFSTR

VDM

+V-BAR APPROACH SCENARIO

YAW REORIENTATION

2. Scenario Description (7)PTV Scenario

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2. Scenario Description (8) ISS Attached and Return Phase

Connections Repressurization of inter volume and

tightness control Hatch opening PTV power down to stand by mode Payload operations PTV power up out of stand by mode Check out Hatch closing Depressurization of inter volume Unlatch Separation Distancing Orbit correction Drift Reentry vehicle power-up (avionics / GNC) Wetting of propulsion system of the reentry

vehicle (pyro valve) Pyros armed Checkout prior to reentry Transfer of the state vector and reentry

information to GNC of reentry vehicle Deorbit impulse Separation of the ATV Propulsion part Separation of the docking adapter

•Checkout prior to reentry•Transfer of the state vector and reentry information to GNC of reentry vehicle •Deorbit impulse•Separation of the ATV Propulsion part•Separation of the docking adapterReentry•Hypersonic flareDescent•Back cover jettison•Parachute sequence deployment •(for instance, extractor, drogue chute, main chute)•Heat shield jettisonLanding•Landing system deployment (airbag)•Touch downVehicle passivation and safingBeacon and post-landing systems deploymentArrival of ground crewManual vehicle safingHatch opening and express payload removalHoisting on transport vehicleTransport

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2. Scenario Description (9)CTV scenario

• Mission Scenario similar To PTV

• Safeguard Scenario during Launch phase

• Two-Failure Tolerance Required

• ATV S/C Modification Analysis led to the Result that it would be the design of a new Vehicle

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ULC Mission Scenario•Launch by Ariane 5 ECA•After nominal separation from AR5 upper stage jettisoning of ULC cover/cargo door•ULC operates in a safe orbit below ISS orbit•ULC conducts ISS approach similar to the ATV after ISS okay•Final Approach differs from ATV due to different docking locations•ULC approach is similar with PTVULC will be docked at Node 2 Port•Exchange of complete platform pallets or of single ORUs by SSRMS and/or Special Purpose Dexterous System•Pallets attachment places are at the truss (starboard, port) via PAS, UCCAS or ULCAS•De-docking Leaving approach ellipsoidBraking manoeuvres for initiating of de-orbiting

2. Scenario Description (10)

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Capsule adaptor module upper I/F close to capsule intermediate diameter,

CoG of capsule close to I/F plane

CoG of complete vehicle below I/F plane

I/F on a 20° cone structure No separation interference

I/F as far as possible from nose (Reentry thermal aspect)

Front docking module

Capsule adapter module

4. PTV System Architect. & ATV S/CModifications (2)

Same configuration for CTV but with Additional redundancies

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4. PTV System Architect. & ATV S/CModifications (3)

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4. CTV System Architect. & ATV S/CModifications (1) Global architecture choice (1)

Capsule adaptor module slightly modified compared to PTV

Same Front Docking module

Emergency Escape module added

Modified Ariane5 fairing added

Vehicle launch with Ariane5 ESC-B (23.0 tons capacity)US-port (V-bar as baseline, -R-bar as back-up treated by delta compared to V-bar)IBDM deviceSame reentry capsule as PTV configuration Autonomous reentry capsule (no power, thermal regulation, … deliveries)No refuel, no reboostNo emergency detachment requirements1 month docking phase

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Blunt Biconic shape launched “nose-down”, 4.4 m ext. diameter, 5 crew member

PC internal volume of 25.8 m³ PC equipment volume 9.1 m³ (preliminary figure) Considering 2 m³ per crew member of free volume, 6.7 m³ can be

occupied by payload. Considering:

20% volume margin to account for secondary structures and packaging factors

payload density of about 300 Kg per cubic meter the theoretical P/L occupying all the residual volume of about 6.7 m³ is 1600 Kg

Considering a Capsule mass of 13.1 tons: The mass w/o P/L is 10.32 tons Potential P/L Mass is 2.78 tons

Also assuming a tilting of 30 deg for seats in landing configuration the biconic shape can easily accommodate a crew of 5

CTV Crew & P/L Accommodation Results (Crew of 5)

4. CTV System Architect. & ATV S/CModifications (5)

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6. ULC System Architect. & ATV S/CModifications (1)

ATV-ULC Layout and Configuration Unpressurized cargo bay Doors jettisoned before circularization Cargo on 2 Express pallets (Boeing)

or ICC pallets (EADS-ST) Front cone with stan-

dard RV equipment and

Common Berthing Mech-

anism (CBM) SSRMS grapple on aft

bay wall